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Analysis of rig test data for an axial/centrifugal compressor in the 12 kg/secExtensive testing was done on a T55-L-712 turboshaft engine compressor in a compressor test rig at TEXTRON/Lycoming. These rig tests will be followed by a series of engine tests to occur at the NASA Lewis Research Center beginning in the last quarter of 1993. The goals of the rig testing were: (1) map the steady state compressor operation from 20 percent to 100 percent design speed, (2) quantify the effects of compressor bleed on the operation of the compressor, and (3) explore and measure the operation of the compressor in the flow ranges 'beyond' the normal compressor stall line. Instrumentation consisted of 497 steady state pressure sensors, 153 temperature sensors and 34 high response transducers for transient analysis in the pre- and post-stall operating regime. These measurements allow for generation of detailed stage characteristics as well as overall mapping. Transient data is being analyzed for the existence of modal disturbances at the front face of the compression system ('stall precursors'). This paper presents some preliminary results of the ongoing analysis and a description of the current and future program plans. It will primarily address the unsteady events at the front face of the compression system that occur as the system transitions from steady state to unsteady (stall/surge) operation.
Document ID
19940029931
Document Type
Conference Paper
Authors
Owen, A. K. (Army Aviation Research and Development Command Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
March 1, 1994
Publication Information
Publication: AGARD, Technology Requirements for Small Gas Turbines
Subject Category
AIRCRAFT PROPULSION AND POWER
Distribution Limits
Public
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